A Large Aspect Ratio Cabin External Folding Wing System

Abstract

The invention discloses a cabin outer folding wing system with a large aspect ratio, which includes a mounting base, a rotating shaft support, a rotating shaft, a shaft end top cover, a spring support, a spring wing, a locking pin assembly, an axial compression spring, and a driving tension spring , Wire rope components. In the initial state, the wings are folded and folded. After the constraint is released, the expansion function of the wings is realized under the action of the driving tension spring and the axial compression spring, and the locking of the unfolded state of the wings is realized through the locking pin assembly. The large-aspect-ratio cabin outer folding wing system of the present invention overcomes the deficiencies in the prior art, and the design process is parameterized, which can be quickly transplanted according to the requirements of different weapon systems, and has a simple mechanism, reliable locking, and outsourcing of the folded state. The network size is small, the unfolded state has a good aerodynamic shape, the mechanism occupies less space inside the cabin, and the working process is smooth and impact-free.

Description

technical field [0001] The present invention relates to a novel large-aspect-ratio cabin external folding wing system, in particular to a projectile external-flap wing deployment system that effectively reduces storage space and greatly increases weapon range, and can be applied to various It can be used for airborne and ground-based tube-launched missiles with wing layout, as well as aircraft with similar aerodynamic shapes such as cruisers and unmanned aerial vehicles. Background technique [0002] In order to meet the operational requirements of standoff strikes and low collateral damage in modern warfare, the range and flight range requirements of flying missiles are constantly increasing. At the same time, weapons should have as compact a structural shape as possible when mounted on a carrier aircraft or launched from the ground. The requirements of long range and small size make more and more combat weapons adopt the layout of folding wings. [0003] Traditional foldi...

AI Technical Summary

Problems solved by technology

The outer envelope size of the horizontal folding method is affected by the wingspan of the projectile, which is not suitable for aerodynamic layout with large aspect ratio

The structural layout of the longitudinal folding method is greatly affected by the chord length of the wings. The longitudinal in-line groove opened on the cabin or the torsion spring mounting seat outside the cabin will have a great impact on the structural strength and aerodynamic shape. The wings also greatly squeezed the interior space of the cabin

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